Aircraft



Dec. 8 1925.

M. PEARSON AIRCRAFT Filed April 27, 1925 4 Sheets-Sheet 1 fi l: 3 7 :-6 I (J0 d is 11611 fan Pg r6021,

Dec. 8, 1925. 1,564,972

M. PEARSON AIRCRAFT I Filed April 27, 1925 4 Sheets-Sheet 4- Inventor. Mirfznjpedrao n1.

.zlorney.

Patented Dec. 8, 1925.

PATENT OFFICE.

KAI-TIN PEARSON, 01' LOS ANGELES, CALIFORNIA.

nrncam.

Application fled April 27, 1826. Serial Ho.26,216.

To all whom it may concern:

Be it known that Man'rm PEARSON, a citizen of the United States, and a resident of Los Angeles, county of Los Angeles, and State of California, has invented a certain new and useful Aircraft; and he does hereby declare that the followin is a full, clear, and exact description t ereof, reference being had to the accompanying drawings, in which like numerals refer to like parts.

This invention relates to improvements in the aircraft shown, described and claimed in the United States Letters Patent No. %,42$2Z,789 that was issued to me June 17,

An object of this invention is to improve d 11-11-of Fi 10 showing a detailed conthe aircraft b providing it with a main an auxiliary he icopter propellers that are arranged to rotate around the same axis and to be driven in opposite directions. 5 1

Another object is to provide a main helicopter propellerthat is constructed and arranged to deflect the displaced air toward the vertical axis of the aircraft.

Another object is to provid the aircraft with an auxiliaryhelicopter propeller that can function as a stabilizer and also prevent a rapid descent of the aircraft when it is in flight and its engine has inadvertently or intentionally stopped.

A feature of invention is shown in the construction and arrangement of the, helicopter propellers and means for supporting and drivingthem.

Other objects, advanta es and features 'of invention may ap ar 'rom the accompanying drawings, t e subjoined description, and the appended claims.

lhe accompanying drawings illustrate the invention.

Figure 1 is a side elevation of the aircraft constructed in accordance with the invention, many of the parts being diagrammatically illustrated.

Fig. 2 is a plan new of the aircraft with many of the parts diagrammatically illustrated.

Fig. 3 is an enlarged fragmental section online3'3ofFig.2. Y f,

Fig. 4 is a fragmental cross section on line 44 of Fig. 3.-

Fig. 5 is a fragmental cross section on line 5-5 of Fig. 4.

F' 6 is an enlarged fra mental section on line 66 of Fig. l wit many of the parts omitted for the sake of clearness.

Fi 7 is a fragmental lan view of the auxi lary helicopter propel er and a portion of the annular rack to which it is connected. Fig. 8 is an enlarged fragmental Section on line 8-8 of Fig. 6, showing a detail of the means for driving the helicopter propellers.

Fig. 9 is a sectional view on a Smaller scale analogous to Fig. 8 showing the means for su porting the floating gears that carry the he icopter. propellers.

Fig. 10 is an enlarged central cross section through the cage for supporting the main helicopter propeller showing one of the propeller blades.

Fig. 11 is a fragmental section on line construction of the flattened tip end of one of the main propeller blades.

, Fig. 13 is an enlarged fragmental section through a ortion of the ca e, showing one of the arc ed ribs to whic the propeller blades are secured.

Fig. 14 is an enlarged fragmental Section through another ortion of the cage, showing one of the tip ends of the propeller blades are secured The main frame 1 comprises the upright channel irons 2 that are spaced equidistant apart and an equal radial distance from a common center; and they are connected tother by plates 3 so that in a plan view t e same is in the form of an octagon.

The frame is additionally braced from the inside by spiders 4.

Adjacent the bottom end of the frame 1 and extending in opposite directionsare the frame extenslons 6, 7 that can be braced and cross braced to form substantial supports.

attened ribs to which the alsothe bottom ends of the channel irons 2 are provided with curved spring legs 8 the she s 12 and 13 to actuate the propel-' lers 14,15, 66 and 67 when they are to be driven.' The construction, operation and arrangement of these propellers and associated parts are substantially like those de- The free ends of the extensions 6, 7 and 1 scribed in the hereinbefore mentioned pats cut, and for the sake of clcarness and brevity a detailed illustration and description of them is omitted.

Also the air compressor 57 and associated parts, together with the air cylinders 49 for actuating the propeller clutches, shown and described in the patent heretofore mentioned, are omitted from these drawings and are not described in this application as the hereinbefore stated improvements do not reside in these features- Brackets 16 are connected to each of the channel irons and the are arranged to support stationary cylin rical supports 17 that have their lower ends threaded into the brackets. .The upper ends of the supports 17 extend through the brackets 18 that are secured to the channel irons 2; and these brackets are provided with hearing boxes 19 in which are mounted guide wheels-20, 21 that are arranged to extend into annular grooves 22 in the under sides of the respective floating gears 23, 24.

Other brackets 25 are secured by nuts 26 to the squared ends of the posts 17 and these brackets are provided with bearing boxes 27 28 in which are arranged the guide wheels 29, 30 that are adapted to be fitted into annular grooves 31 in the top sides of the floating gears 23, 24 and these parts are arranged so that the gears 23, 24 can be rotated around a common axis and in opposite directions; and the. gears lie in the sameplane with the gears 23 within the gear 24.

The means for driving the floating gears 23, 24 is best shown in Fig. 8. As seen therein a hollow shaft 32 is loosely fitted over one of the supports 17 and is provided with roller bearings 33, 34 in the brackets 16, 18; a ball bearing 35 in .a bracket 36 and another roller 37 interposed between the upper end of the post 17 and the hollow shaft bywhich means the shaft is rotatably held in a vertical position.

A pinion 38 is secured to the upper end of the shaft 32 and arranged to engage the teeth of the floating gears 23, 24 so that when the pinion is driven the gears will be rotated in opposite directions.

The hollow shaft 32 is driven by means of a bevel ear 39 on shaft 13 engaging another bevei gear 40 that is secured to the shaft 32 so that when the shaft 13 is ac tuated the annular gears 23, 24 will be rotated. The shaft 13 can be driven by the engine 9.

A cage 41 is secured to the floating gear 23; and to this cage is secured the main helicopter propeller 42 that corresponds in construction and operation to the propeller 20 shown and described in the patent hereinbefore mentioned; and this propeller is driven in the direction of the arrows 12 shown in Flg. 2. The cage 41 is formed of a number of vertical rods 43 that have their lower ends bolted to aflange 44 that is integral with the gear 23, and the upper ends of these rods terminate in ribs 45.

The ribs 45 vary in their formation, as illustrated in Figs. 13 and 14. Ribs 45, such as shown in Fig. 13, are arran ed at the advanced ends of the propeller blades and the other ribs, such as shown in Fig.

14, are arranged at the rear end thereof,

with the intermediate ribs gradually deranged below and extends beyond the main propeller 42 and is supported on and driven y the gear 24.

Spokes 51 have their ends threaded into bosses 52 on the outer periphery of the gear 24 and to the outer end portions of the spokes an annular sheet metal disk 53 is secured by welding as indicated in Figs. 3, 4 and 5. The disk 53 is provided with vanes 54 that are constructed and arranged to defleet the air from the top through openings 56 to the under sideof the disk when it is driven in the direction of the arrows a shown in Fig. 2. g

Trap doors 55 are pivotally mounted on loose portions of the ribs 51 and are arranged under the vanes 54 and are normally held in a closed position by springs 57. These springs yield when the disk 53 is rotated so that the trap doors will open to permit air to pass from the too to the underside thereof whereby the disk and associated parts function as an auxiliary helicopter propeller.

The primary purpose of the disk 53 is to provide a stabilizer that will aid in holding the aircraft in an upright'positio-n and will also prevent a rapld descent in the event that the helicopter propellers are either intentionally or accidentally brought to rest. In other words the trap doors 55 close when the aircraft starts to descend so that the disk presents a large air resistance surface to retard its descent. Also in descending part of the displaced airvwill be forced outward around the annular edge of the disk and another volume of the air will be forced in wardly to contact with the extensive under surface of the main propeller, thereby stabilizing the aircraft in an upright position as Well as retarding its descent.

I claim:

1. The aircraft set forth comprising a frame; supports arranged around and at-' tached to said frame; guide wheels carried by said supports; inner and outer floating and propeller means attached to said gears for lifting said aircraft when said gears are driven. t

2. The aircraft set forth comprising a frame; vertical supports arranged aroundand attached to said frame; bearings secured to said supports and frame; guide wheels in said bearings; inner and outer floating gears arranged in the same plane that are guided and supported by said wheels; means for rotating said gears around a common axis and in opposite directions; vertical rods secured.

to said inner gear; horizontal spokes secured to said outer gear and propeller means attached to said rods and spokes for lifting said air craft when said gears are driven.

3. The air craft set forth comprising a frame, vertical supports spaced equidistant around and attached to said frame; bearings secured to said supports and frame; guide wheels in said bearings; an outer floating gear and an inner gear within the outer gear that are supported by said wheels and alsoarranged to rotate around a common axis;

vertical rods secured to said inner gear; a

helicopter propeller attachedto said rods; horizontal spokes secured to said'outer gear; van auxiliary helicopter-propeller secured to said spokes; a pinion for driving said floating gears in opposite directions; and means for driving said pinion.

4.- The aircraft set 'forth comprising a frame; supports spaced equidistant around and attached to said frame; bearings secured to said supports and frame; guide wheels in said bearings; lnner" and 0l1tGI-,fl0itt1n gears supported-by said wheels; a vertlca cage supported. by said inner gear; a main helicopter propeller secured to said cage;

spokes secured to said outer gear; and an auxiliary helicopter propeller secured tosaid spokes. v

5. The aircraft set'forth comprising a frame; supports spaced around and attached to said frame; guide wheels on said su wheels; spokes secured to said gear; an annular disk secured to said spokes; vanes integralwith said disk that are adapted to deflect air downward through openings in said disk; and means for driving said gear to rotate-said disk.

6. The aircraft set forth comprisin a frame; supports spaced around and attac ed to said frame; guide wheels on said su ports; a floating gear supported by said wheels; spokes secured 'to said gear; an annular disk secured to said spokes; vanes integral with said disk that are adapted to -defleet air downward through openings in said disk; trap doors for closing the1openings aflixed my signature.

MARTIN PEARSON.

ports; a floating gear supported bysald 

